CN107176297A - A kind of aircraft - Google Patents
A kind of aircraft Download PDFInfo
- Publication number
- CN107176297A CN107176297A CN201710471949.3A CN201710471949A CN107176297A CN 107176297 A CN107176297 A CN 107176297A CN 201710471949 A CN201710471949 A CN 201710471949A CN 107176297 A CN107176297 A CN 107176297A
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- Prior art keywords
- fuselage
- wing
- aircraft
- tilting wing
- rotor
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- 230000000694 effects Effects 0.000 claims abstract description 8
- 230000001360 synchronised effect Effects 0.000 claims description 5
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 230000002457 bidirectional effect Effects 0.000 abstract description 13
- 238000000034 method Methods 0.000 abstract description 3
- 238000012546 transfer Methods 0.000 abstract description 2
- 238000012544 monitoring process Methods 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 238000003786 synthesis reaction Methods 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8254—Shrouded tail rotors, e.g. "Fenestron" fans
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The present invention relates to flight domain.The invention provides the new wing VTOL craft that verts that a kind of afterbody is equipped with bidirectional propulsion shrouded propeller；Aircraft fuselage of the present invention is provided with two quick boosting conduits that take off, and bottom both sides are provided with longitudinally through edge strip；Wing is fixedly mounted four lifting propellers before and after aircraft, and can be realized by the sychronisation of fuselage both sides VTOL and the flat front and rear wing for flying transfer process synchronously vert.The present invention ensures effective control in aircraft direction in hovering and state of flight by afterbody bidirectional propulsion shrouded propeller；Boosting conduit also realizes the quick accelerated take-off on land and warship as the buttress brace of complete machine using fast gas assist device；Aircraft bottom longitudinal direction edge strip coordinates expanded letter fuselage to also increase the lift put down when flying while ground cushioning effect is effectively increased.Main wing bottom is provided with tilt protection wheel before wing, and wing tip contacts to earth when preventing landing roughly and meeting extreme crosswind.
Description
Technical field
The invention belongs to flight domain, it is related to a kind of vert wing VTOL of afterbody equipped with bidirectional propulsion shrouded propeller and flies
Row device.
Background technology
The current various axle aircraft species of VTOL 4~8 are various, and it completes short distance, fixed point, low speed task side
Just, most times are in floating state during but because of its work, and engine power load is low (being less than 5kg/kW), and power consumption is big, it is impossible to
Remote, long endurance work is realized, and horizontal flight speed is limited.
Fixed wing aircraft with wing load level flying method due to being run mostly, its power loading (15~20kg/kW)
Far above Multi-axis aircraft, this is also that all kinds of Multi-axis aircrafts are incomparable.Fixed wing aircraft is more with the same terms
Axle machine is compared, and power loading wants high 3~4 times, that is to say, that the electric energy of same multiple can be saved under the same conditions when flying by putting down.
The shortcoming of all vertical flight devices maximum in addition to wing formula of verting is exactly that the power loading of engine is low, Nai Zhifei
Row distance and limited speed, and the helicopter for wing mode of verting can not only realize VTOL, can also be in identical weight and electric energy
Under conditions of realize the flight of relatively remote longer endurance and more speed.
The content of the invention
Course of new aircraft provided by the present invention, can realize VTOL on land and warship, and with endurance length, speed
It is high, can realize the quick accelerated take-off on land and warship when coordinating special fast gas assist device and directly be turned by climbing
Enter to put down and fly state.
The present invention aircraft without airport, can the VTOL on land or warship, most times are with horizontal during work
State is flown, and in-flight using the two-way propulsion shrouded propeller of afterbody controls in hovering and effectively heading, with it is quick
Combustion gas assist device can be realized when coordinating it is carrier-borne quickly take off, to complete various monitoring tasks, particularly carrier-borne examine beats integrated
Comprehensive task.
The aircraft of the present invention includes fuselage, and the fuselage is equipped with front and rear four machines that vert for carrying lifting propeller
The wing, first can tilting wing with second can tilting wing it is coaxial；3rd can tilting wing with the 4th can tilting wing it is coaxial, four
Lifting propeller with four can tilting wing to be fixedly connected, each lifting propeller drives by motor；The aircraft tail
Portion is equipped with non-activity rudder face vertical tail, and the vertical tail bottom is vertical with heading to be provided with bidirectional propulsion shrouded propeller,
To realize aircraft hovering and direction controlling in-flight；The bottom of the fuselage is provided with tricycle landing gear, on ground
When parked, underbelly and horizontal plane angle 2-3 degree, this is maximum lift-drag ratio angle of attack when fuselage slides race and flight.
Wherein, two sychronisations are installed outside the fuselage both sides, four can be realized in 90 degree and carries lift spiral shell
Rotation oar can tilting wing complete it is synchronous vert, to realize the conversion of VTOL and horizontal flight.
Wherein, the fuselage side is aerofoil profile fairing, to constitute lift fuselage.
Wherein, the bottom both sides of the fuselage are mounted on longitudinally disposed flat ventral edge strip, the ventral edge strip with
Horizontal plane angle is 30 degree.
Wherein, the fuselage is provided with two boosting conduits, and the boosting conduit is along from the fore-body to rear portion
Direction extends.
Wherein, the upper surface of the fuselage is provided with umbrella storehouse of saving oneself.
Wherein, the bottom of two lifting propellers in front side is equipped with slant protection wheel, the slant protection wheel and the side
Main landing gear wheel touchdown point angle is not less than 8 degree, and the wing tip ground height of the lifting propeller is not less than 6cm.
Flying instrument of the present invention has the advantages that：
Aircraft of the present invention can realize VTOL on land and warship, and with endurance length, speed height and take off quick
Advantage.The present invention aircraft without airport, can the VTOL on land or warship, most times are with horizontality during flight
Flight, and ensure hovering and effective control in state of flight direction using the two-way shrouded propeller of afterbody, it can complete each
Monitoring task is planted, particularly carrier-borne examine beats integrated synthesis task.
It should be appreciated that the general description of the above and detailed description hereinafter are only exemplary and explanatory, not
Can the limitation present invention.
Brief description of the drawings
Technical scheme in order to illustrate the embodiments of the present invention more clearly, below will be to embodiment or description of the prior art
In required for the accompanying drawing that uses be briefly described.
Fig. 1 is the schematic side view that aircraft ground of the present invention parks (or take off vertically, hover) posture；
Fig. 2 is the schematic top plan view that aircraft ground of the present invention parks (or take off vertically, hover) posture；
Fig. 3 is the front-view schematic diagram that aircraft ground of the present invention parks (or take off vertically, hover) posture；
Fig. 4 is the front-view schematic diagram of the horizontal flight attitude of aircraft of the present invention；
Fig. 5 is the schematic top plan view of the horizontal flight attitude of aircraft of the present invention；
Fig. 6 is the schematic side view of the horizontal flight attitude of aircraft of the present invention；
Fig. 7 is that aircraft ground of the present invention slides the schematic side view for running (overload) take-off attitude.
Description of reference numerals：
1 photoelectric nacelle
2 fuselages
3 first rotors
4 first motors
5 save oneself umbrella storehouse
6 the 3rd rotors
7 vertical tails
8 horizontal tail vanes
9 shrouded propellers
Undercarriage after 10
11 ventral edge strips
12 nose-gears
13 boosting conduits
14 first can tilting wing
15 the 3rd can tilting wing
16 gps antennas
17 synchronising (connecting) rods
18 slant protection wheels
19 the 3rd motors
20 axis
21 second rotors
22 the 4th rotors
23 second can tilting wing
24 the 4th can tilting wing
25 second motors
26 the 4th motors
Embodiment
Embodiments of the invention are introduced below in conjunction with the accompanying drawings.
As shown in figs. 1-7, aircraft of the invention includes fuselage 2, and fuselage 2 carries lifting propeller equipped with front and rear four
Can tilting wing, first can tilting wing 14 with second can tilting wing 23 it is coaxial；3rd can tilting wing 19 can incline with the 4th
The wing 24 of making a connection is coaxial, four lifting propellers with four can tilting wing be to be fixedly connected, each lifting propeller is by motor
Driving；Aircraft afterbody is equipped with the vertical tail 7 of non-activity rudder face, and the bottom of vertical tail 7 is vertical with heading provided with double
To thrust shrouded propeller 9, to realize aircraft hovering and direction controlling in-flight；The bottom of fuselage 2 is provided with first three
Point undercarriage, when ground is parked, the bottom of fuselage 2 and horizontal plane angle a are 2-3 degree, this be fuselage slide run and during flight it is maximum
The lift-drag ratio angle of attack.
The present invention aircraft without airport, can the VTOL on land or warship, most of time is with level during work
State is flown, and using afterbody bidirectional propulsion shrouded propeller 9 ensure hovering and during state of flight direction effective control,
A variety of monitoring tasks can be completed, particularly carrier-borne examine beats integrated synthesis task.The vertical tail 7 of aircraft afterbody of the present invention is only
If one fixes rudder face and the two-way shrouded propeller 9 of minor diameter controllable thrust, using can rapid translating thrust direction bidirectional propulsion
Shrouded propeller 9 effectively realizes direction controlling when hovering and flight.In one embodiment of the invention, aircraft for example may be used
Think that a kind of afterbody is equipped with the wing VTOL helicopter that verts of bidirectional propulsion shrouded propeller.
Embodiments of the invention are described in detail below.
In one embodiment of the invention, as shown in Fig. 2 the axis 20 of fuselage 2 extends to fuselage from the front portion of fuselage 2
2 rear portions, a side of fuselage 2 be provided with first can tilting wing 14 and the 3rd can tilting wing 15, another side is installed
Have second can tilting wing 23 and the 4th can tilting wing 24, first can tilting wing 14 and the 3rd can be during tilting wing 15 be located at
The side of axis 20, second can tilting wing 23 and the 4th can tilting wing 24 be located at axis 20 opposite side.First can incline
The motor 4 of first rotor (lifting propeller) 3 and first is installed, first motor 4 drives the first rotor 3 on the favourable turn wing 14, the
One can tilting wing 14 and the first rotor 3 to be fixedly connected.Second can be provided with the second rotor (lift spiral on tilting wing 23
Oar) 21 and second motor 25, second motor 25 drives the second rotor 21, second can the rotor 21 of tilting wing 23 and second be solid
Fixed connection.3rd can be provided with the 3rd rotor 6 (lifting propeller) and the 3rd motor 19, the 3rd motor 19 on tilting wing 15
Drive the 3rd rotor 6, the 3rd rotor 6 with the 3rd can tilting wing 15 to be fixedly connected.4th can be provided with tilting wing 24
4th rotor 22 (lifting propeller) and the 4th motor 26, the 4th motor 26 drive the 4th rotor 22, and the 4th can tilting wing
24 be to be fixedly connected with the 4th rotor 22.First can tilting wing 14 and second can tilting wing 23 be located at the forward position of fuselage 2,
3rd can tilting wing 15 and the 4th can tilting wing 24 be located at the rear positions of fuselage 2.First can the rotation of tilting wing 14 and first
The wing 3 together verts, second can tilting wing 23 together verted with the second rotor 21, the 3rd can the rotor 6 of tilting wing 15 and the 3rd
Together vert, the 4th can tilting wing 24 together verted with the 4th rotor 22.Below by first can tilting wing 14 and second can
Tilting wing 23 be collectively referred to as before can tilting wing, by the 3rd can tilting wing 15 and the 4th can tilting wing 24 be collectively referred to as after can incline
The favourable turn wing, preceding rotor is collectively referred to as by the first rotor 3 and the second rotor 21, is revolved after the 3rd rotor 6 and the 4th rotor 22 are collectively referred to as
The wing is described.As Figure 1-3, when aircraft vertical takes off or hovers, preceding rotor and rear rotor are provided for aircraft and risen
Power, as Figure 4-Figure 6, when aircraft horizontal flight, preceding rotor and rear rotor provide the pulling force of flight forward for aircraft, such as
Shown in Fig. 7, when aircraft ground rolling start, preceding rotor and rear rotor provide lift and pulling force for aircraft, short to realize
Away from rolling start.
The both sides external of fuselage 2 is provided with two identical synchronising (connecting) rods 17, and the connection of synchronising (connecting) rod 17 first can vert machine
The wing 14 and the 3rd can tilting wing 15, opposite side synchronising (connecting) rod 17 connection second can tilting wing 23 and the 4th can tilting wing
24.In one embodiment of the invention, synchronising (connecting) rod 17 and first can tilting wing 14 and the 3rd can be between tilting wing 15
Connected for axle, the opposite side synchronising (connecting) rod 17 of fuselage 2 and second can tilting wing 23 and the 4th can connect between tilting wing 24 for axle
Connect, first can tilting wing 14 and second can tilting wing 23 it is coaxial, the 3rd can tilting wing 15 and the 4th can tilting wing 24
Coaxially.One synchronising (connecting) rod 17 drives first can tilting wing 14 and the 3rd can tilting wing 15 be synchronous verts.Fuselage opposite side
Synchronising (connecting) rod 17 drives second can tilting wing 23 and the 4th can tilting wing 24 be synchronous verts.The angle that synchronising (connecting) rod 17 is rotated
B is 90 degree.As Figure 1-3, when aircraft vertical takes off or hovers, the line of pull direction of preceding rotor and rear rotor it is vertical to
On, as Figure 4-Figure 6, when aircraft horizontal flight, preceding rotor and rear rotor thrust line are horizontal forward, as shown in fig. 7, when winged
When row device ground roll-out is taken off, preceding rotor and rear rotor thrust line are in 40 degree of angle oblique pull states, that is to say, that aircraft of the present invention
In different mode of operations, preceding rotor is different with rear rotor thrust line direction, when aircraft is changed between different working modes
When, the inclination angle and rotating speed of preceding rotor and rear rotor will also change.The rotation of synchronising (connecting) rod 17, which can be achieved to drive, first can vert machine
The wing the 14, the 3rd can tilting wing 15, second can tilting wing 23 and the 4th can tilting wing 24 vert, so as to drive the first rotor
3rd, the second rotor 21, the 3rd rotor 6 and the 4th rotor 22 vert, so that the first rotor 3, the second rotor 21, the 3rd rotor 6 and
The state change of four rotors 22.The acting as of synchronising (connecting) rod 17 makes the first rotor 3, the second rotor 21, the 3rd rotor 6 and the 4th rotation
The wing 22 changes acting in agreement for state, synchronously verts.The first rotor 3, the second rotor 21, the 3rd rotor 6 and the 4th of the present invention
Rotor 22 can synchronously realize 90 degree and vert, and flat winged conversion is transitioned into by taking off vertically to complete aircraft.
As shown in figs. 1-7, aircraft of the invention includes fuselage 2, and fuselage 2 is expanded letter fuselage, generally flat, front portion
It is arc with rear portion, the side of fuselage 2 is aerofoil profile fairing, to constitute lift fuselage.As shown in figure 1, the resistance that most rises higher of fuselage 2
It is 2-3 degree than angle of attack a, maximum lift-drag ratio angle of attack a is underbelly and the angle of level ground.In one embodiment of the present of invention
In, maximum lift-drag ratio angle of attack a is 2.5 degree.The fuselage 2 of the present invention is run in horizontal flight with maximum lift-drag ratio angle of attack a, this
The fuselage 2 of an invention not still effective lifting body, also provides enough spaces to set up hydrogen fuel cell system in machine,
Make it possible that carrier-borne electric airplane reaches the flight time of more than 4 hours.
The head of fuselage 2 is provided with photoelectric nacelle 1, photoelectric nacelle 1 and is provided with multiple sensors, for completing related sky
Middle scouting or strike mission.
The rear upper surface of fuselage 2 is provided with the vertical tail 7 of non-activity rudder face, the bottom of vertical tail 7 and heading
Vertically it is provided with duct, duct and bidirectional propulsion shrouded propeller 9 is installed.The effect one of vertical tail 7 is to install bidirectional propulsion
Shrouded propeller 9, two be the control direction in aircraft horizontal flight.Wherein, bidirectional propulsion shrouded propeller 9 produces Bidirectional pulling
Power, to realize the control in aircraft direction when hovering or being flat winged.The rotary inertia of bidirectional propulsion shrouded propeller 9 of the present invention
It is small, reversion quickly can be switched to from rotating forward, or quickly switch to rotating forward from reversion, it is ensured that aircraft is in hovering and flight shape
Effective control in direction during state.Aircraft of the present invention eliminates the rudder control surfaces of general aircraft, simplifies structure, alleviates
The weight of aircraft, and in hovering, turn to match somebody with somebody with two diagonal rotor motor differences by bidirectional propulsion shrouded propeller 9
Close, effective control in the direction under hovering posture can be completed.
The afterbody of fuselage 2 is provided with horizontal tail vane 8, and horizontal tail vane 8 is used for the control of the horizontal flight attitude of aircraft, such as schemed
Shown in 1, the anglec of rotation c of horizontal tail vane 8 is ± 25 degree, that is to say, that horizontal tail vane 8 can rotate up 25 degree, can also
It is rotated down 25 degree.
The underside of forward of fuselage 2 is provided with the downside of nose-gear 12, the rear portion of fuselage 2 and is provided with rear undercarriage 10.
The both sides of the bottom of fuselage 2 are mounted on longitudinally disposed flat ventral edge strip 11, and ventral edge strip 11 is strip.Such as
Shown in Fig. 2, two ventral edge strips 11 are located at the side lower part of fuselage two, in one embodiment of the invention, the slave of ventral edge strip 11
The head of body 2 extends to the afterbody of fuselage 2.Aircraft is in flat fly, and ventral edge strip 11 can increase lift；Aircraft is vertical
When taking off or hovering, ventral edge strip 11 can be effectively increased cushioning effect.In one embodiment of the invention, such as Fig. 3 and Fig. 4
Shown, ventral edge strip 11 is tilted down, and such ventral edge strip 11 can effectively improve the performance of aircraft vertical landing.In the present invention
Another embodiment in, the angle of ventral edge strip 11 and the bottom surface of expanded letter fuselage 2 is 30 degree.
Fuselage 2 is provided with two boosting conduits 13, and the front portion of boosting conduit 13 from fuselage 2 extends to the rear portion of fuselage 2.One
Aspect boosting conduit 13 is the insertion buttress brace of fuselage 2, while also making the structure of fuselage 2 be strengthened；On the other hand boosting is passed through
The cooperation of conduit 13 and the quick assist device of lightweight internal combustion, aircraft (or land) can realize that 60 degree of elevations angle are quickly helped on warship
Boost it is winged, enter after taking off climb and switch to it is flat fly, not only shorten take off be transformed into it is flat fly over journey the time required to, Er Qieyou
Effect reduce the electric energy that transfer process is consumed, add voyage so that aircraft of the present invention be adapted to complete fleet warning, in
After multiple-tasks such as communication, convoys.
The middle part upper surface of fuselage 2 is provided with umbrella storehouse 5 of saving oneself, when running into extreme case, and umbrella storehouse 5 of saving oneself can be opened, bullet
Go out umbrella of saving oneself, it is ensured that aircraft security is reclaimed.
As shown in figure 3, the bottom of the first rotor 3 and the second rotor 21 is equipped with slant protection wheel 18, to prevent drop roughly
Wing tip contacts to earth when falling and meeting extreme crosswind.In one embodiment of the invention, as shown in figure 3, the slant protection wheel 18 and the side
Main landing gear wheel touchdown point angle is not less than 8 degree, that is to say, that the slant protection wheel 18 contacts to earth with the side main landing gear wheel
The line of point (i.e. the touchdown point of the wheel of undercarriage 10 behind the side) and the angle of level ground are not less than 8 degree, to prevent wing tip from touching
Ground.
As shown in figure 1, GPS (Global Positioning System, global positioning system) is additionally provided with fuselage 2, with
Realize the positioning of aircraft.
As shown in fig. 7, when aircraft is had ready conditions and taken off in airfield runway cunning race mode, the main shaft of the first rotor 3, second
The minimum angle of the main shaft of rotor 21, the main shaft of the main shaft of the 3rd rotor 6 and the 4th rotor 22 and level ground must not be less than 40
Degree, to avoid lifting propeller wing tip from contacting to earth, now, the wing tip of four lifting propellers and the minimum range on ground are 6cm.
The present invention is that a kind of realized with carrier-borne (without special airport) VTOL and under thruster specialized is quickly risen
Winged aircraft, the institute that decapacitation completes helicopter is functional outer, and most times are with the new of fixed-wing mode high-speed horizontal flight
Type aircraft, aircraft of the invention for example can be electronic unmanned plane.
In the present invention, term " first ", " second " are only used for the purpose described, and it is not intended that indicating or implying phase
To importance；Term " multiple " then refers to two or more, unless otherwise clear and definite restriction.Term " installation ", " connected ",
The terms such as " connection ", " fixation " all should be interpreted broadly, for example, " connection " can be fixedly connected or detachably connect
Connect, or be integrally connected；" connected " can be joined directly together, and can also be indirectly connected to by intermediary.For this area
For those of ordinary skill, the concrete meaning of above-mentioned term in the present invention can be understood as the case may be.
In description of the invention, it is to be understood that the orientation or position relationship of the instruction such as term " on ", " under " be based on
Orientation shown in the drawings or position relationship, are for only for ease of the description present invention and simplify description, rather than indicate or imply institute
The device or unit of finger must have specific direction, with specific azimuth configuration and operation, it is thus impossible to be interpreted as to this hair
Bright limitation.
In the description of this specification, the description of term " one embodiment ", " some embodiments ", " specific embodiment " etc.
Mean that combining the embodiment or specific features, structure, material or the feature of example description is contained at least one reality of the invention
Apply in example or example.In this manual, identical embodiment or reality are not necessarily referring to the schematic representation of above-mentioned term
Example.Moreover, description specific features, structure, material or feature can in any one or more embodiments or example with
Suitable mode is combined.
Described above is only the embodiment of the present invention, is made skilled artisans appreciate that or realizing this hair
It is bright.A variety of modifications to these embodiments will be apparent to one skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore it is of the invention
The embodiments shown herein is not intended to be limited to, and is to fit to and principles disclosed herein and features of novelty phase one
The most wide scope caused.
Embodiment of the present invention above, is not intended to limit the scope of the present invention..
Claims (7)
1. a kind of aircraft, it is characterised in that including fuselage, the fuselage is equipped with front and rear four inclining with lifting propeller
Make a connection the wing, first can tilting wing with second can tilting wing it is coaxial；3rd can tilting wing with the 4th can tilting wing it is coaxial,
Four lifting propellers with four can tilting wing to be fixedly connected, each lifting propeller drives by motor；
The aircraft afterbody is equipped with non-activity rudder face vertical tail, and the vertical tail bottom is vertical with heading provided with two-way
Thrust shrouded propeller, to realize aircraft hovering and direction controlling in-flight；
The bottom of the fuselage is provided with tricycle landing gear, when ground is parked, underbelly and horizontal plane angle 2-3 degree,
This is maximum lift-drag ratio angle of attack when fuselage slides race and flight.
2. aircraft according to claim 1, it is characterised in that two synchronous dresses are provided with outside the fuselage both sides
Put, can realize in 90 degree four with lifting propeller can tilting wing complete it is synchronous vert, with realize VTOL with
The conversion of horizontal flight.
3. aircraft according to claim 2, it is characterised in that the fuselage side is aerofoil profile fairing, to constitute liter
Power fuselage.
4. the aircraft according to any one of claim 1-3, it is characterised in that the bottom both sides of the fuselage are respectively mounted
There is longitudinally disposed flat ventral edge strip, the ventral edge strip is 30 degree with horizontal plane angle.
5. the aircraft according to any one of claim 1-3, it is characterised in that the fuselage is led provided with two boostings
Pipe, the boosting conduit extends along from the fore-body to the direction at rear portion.
6. the aircraft according to any one of claim 1-3, it is characterised in that the upper surface of the fuselage is provided with certainly
Rescue umbrella storehouse.
7. the aircraft according to any one of claim 1-3, it is characterised in that the lifting propeller of front side two
Bottom is equipped with slant protection wheel, and the slant protection wheel is not less than 8 degree, the liter with the side main landing gear wheel touchdown point angle
The wing tip ground height of wrench of a force system oar is not less than 6cm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710471949.3A CN107176297A (en) | 2017-06-20 | 2017-06-20 | A kind of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710471949.3A CN107176297A (en) | 2017-06-20 | 2017-06-20 | A kind of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107176297A true CN107176297A (en) | 2017-09-19 |
Family
ID=59845271
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710471949.3A Pending CN107176297A (en) | 2017-06-20 | 2017-06-20 | A kind of aircraft |
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| Country | Link |
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| CN (1) | CN107176297A (en) |
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| CN108248314A (en) * | 2018-01-18 | 2018-07-06 | 仲恺农业工程学院 | Air-ground dual-purpose four-rotor aircraft |
| CN108639331A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | One kind is verted double-rotor aerobat |
| CN109398691A (en) * | 2018-12-29 | 2019-03-01 | 保定维特瑞光电能源科技有限公司 | A kind of vertically taking off and landing flyer becoming flying angle |
| CN110654534A (en) * | 2018-06-29 | 2020-01-07 | 中光电智能机器人股份有限公司 | Rotorcraft |
| CN110901906A (en) * | 2019-12-04 | 2020-03-24 | 中国直升机设计研究所 | Ground effect rotor craft and flight mode switching method |
| CN113734423A (en) * | 2021-10-21 | 2021-12-03 | 兰州山河上空智能科技有限公司 | L-shaped structure vertical take-off and landing flight mechanism, unmanned aerial vehicle and aircraft |
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| CN113734423A (en) * | 2021-10-21 | 2021-12-03 | 兰州山河上空智能科技有限公司 | L-shaped structure vertical take-off and landing flight mechanism, unmanned aerial vehicle and aircraft |
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